Automatic safety device or stabilizer for heavier-than-air flying-machines.



Wf SAINT'. AUTOMATIC SAFETY DEVICE 0R STABILIZER FOR AHEAVIER-'IHAN-AIR. FLYING MACHINES. l

v APPLICATION FILED DEG. 4, 1911.

Patented Jan. 14, 1913.

W. SAINT. AUTOMATIC SAFETY DEVICE CR STABILIZER TOR HBAVIBR-THAN-Am FLYING MACHINES.

, APPLICATION FILED DEG. 4, 1911.` l

Patented Jan. 14, 1913.

3 SHEETS-SHEET 2.

aan,

W. SAINT. AUTOMATIC SAFETY DEVICE OR STABILIZER POR HEAVIER-THAN-AIR FLYING MACHINES.

APPLIUATIQN FILED DEC. 4, 1911.

Patented Jan. 14,1913.

' 3 SHEETS-'SHEET UNITED sfrnfrns WILLIAM SAINT, F DAYTON, OHIO.

rnrinvr OFFICE.

i AUTOMATIC SAFETY DEVICE 0R STABILIZER FOR HEAVIER-THAN-AIR :FLYING-` i MACHINES. 4 i

To all who/m, may concern:

Be it known that I, VILLIAM SAINT, citizen of the United; States, residing at Dayton,in the county of Montgomery andfState of Ohio,.have invented certain new and use-A ful Improvements in Automatic Safety Devices or Stabilizers for Heavier-'Ihan-Air Flying-Machines; and I do declare the following to be a full, clear, and exact descrip@ tion of the invention, such as will enable others skilled in the art to which it appertains to make and use the same, `reference being had to the accompanying drawings, and to the letters and figures of reference marked thereon, which form a part of this specification.`

i This `inventionwrelates to new and useful improvements in automatic safety devices or i' `stabilizers for heavier-than-.air flying ma' chines, and has vto do particularly with means for balancing the flying` machine when in mid-air. a

The object of the invention is. to provide Y a device of the above type by means of which a flying machine will be prevented from careening and turning up side down in mid-air, thereby preventing accidents so common in aerial navigation.

' Referring to accompanying drawings, Figure 1 is a longitudinal sectional eleva tion through the center of a liying machine, showing my invention applied thereto, the

view being onthe line a-a of Fig. 2; Fig. 2

is a lateral section on the line b-b of Fig. 1, showing thel balancing lever in a dropped or extended position. Fig. 3 is a vertical longitudinalsectional elevation through the' balancing lever, Vthe same being shown in a telescopedvor contracted position; Fig. Ll is a section on the line o-o of Fig. 3; Fig. 15 1s a front elevation of the universal pivot for y theV balancinglever shown in Fig. 3; Fig. 6 is a top plan view of Fig.'5; Fig. 7 is a deofFig. 3; and Fig. 14 is a detail View of the Patented Jan. 14,1913.

`Application. filed December 4,1911. Serial No.V 663,693..

ratchet which holds theweight `in an elevated' position.

The` aeroplane, to which my invention may be applied, may be of any type, either monoplane or biplane. In the drawings, I have shown the invention applied to a well known type of biplane, which consists of an rupper plane 1, and a lower plane 2, which are separatedby struts 3 and braced by guy wires 4. lIn the present case, the aeroplane is mounted on skids 5, and is provided with an elevator 6, and a rudder 7. In aeroplanes of kall types, it is found convenient to` construct them with a high center of gravity, which permits them to be easily lowing balancingdevice is provided. See.

Figs. l, 2 and 3.

The lower plane 2 is provided with an opening 9 in exact vertical alinement with the center of gravity of the machine. Extending through said opening 9 is a telescopic device consisting of an upper and outer tubular member lO, and any desired number of lower and inner members 11, 12 and 13, which may be of any length. The upper outer member 10 is pivoted to the `lower plane 2, andV is provided with "trunnions 14 j ournaled in a swinging frame 15. The frame `15 is provided wit-h trunnions 1G journaled invbearings 17 attached to the lower plane 2. By this construction, the

upper member 10 and the lever as awhole is universally pivoted tothe lower plane and may swing in any direction relative to the machine. The upper. end of the outer member 101s connected to any points on the aeroplane, such as the upper ends of the struts 3, by loose or flexible connections 18, which permit the `said lever lto swing on the pivots or fulcrums 14 andz16,findependently of the craft. The inner members 11, 12 and 13 are provided with elongated offsets or lugs .'19 adapted to `engage flanges 20 on the next adjacent outer members l0, 11 and 12` to limit the downward movement ofthe inner members, and. to hold. ,the memhersn an assembled position when extended. The lugs 19 are of a length suicient to hold the lever rigid when extended.H Theiower end Of--theeitreme rlrler telescopic member 13. is provided with a weight 21, which VYtogether with the inner memloers 11, 12 and 13', is elevated when the leveris to-` be placed out of use or telescoped by thefollowing device. The upper end ofthe inner member 13 is provided with an eyelet 2 2 to which a cable 23 is attached. The cable 23 extends upwardly and overa sheave 24, journaled on the outermostmember 10, and thence vdownwardly and around a spool 25l The spool such position bythe pawl 3l and ratchet 30. Y

The pawl 31 is provided with an operating handle 34 and is held ina position out of engagement with the `ratchet 30 by a spring 35, which engages lugs 35a. The weight of the handle 34 is suflicient to hold the pawl in engagement with the ratchet. Y

When the aviator is unable to manage 'the machine by means ofthe elevator 6 and Vrudder'?, and there is danger of the-machine turning over, the operator' releases the weight 21 by shifting the handle 34 and dis, engaging the pawl 31 and ratchet 30.. The weight 21 will fall by gravity, thereby changing or lowering'the center of gravity of the machine. The momentum or impact of `the falling weight and telescopic members is arrested by a cushion or spring 36,

attached to a bracket 37 extending from the member 10, and to a bracket 38 extending from the member 11. The spring -36 yis placed in the rear of the lever as a whole to eliminate unnecessary air Y resistance. When-the weight is in alowered position, it is adapted to exert a leverage on the machine, which maintains itin a state of equipoise or even balance. When the machine hasa tendency to careen. to one side, or to the front or rear, the weight will be moved in the opposite direct-ion, and, being under the influence of gravity, will exert a'force tending to move the aeroplane to a: stable position. The lever, formedby the members 10, 11 12 and 13, may be of any suitable length, and the .weight 21 may be Vof any suitablel form or size, which proportions may be determined by thesize of themachine. The object in permitting the said lever to have a slightv movement independent of theY aeroplane, is to permit the `aeroplane to beunder the control of the elevator 6 and rudder- 7, when, the machine isi-lying under ideal orv normal conditions, and the weight 2 1 is lowered. The extent of this independent movement may be varied by'adjusting ,the vlength ofthe lexiblereenneetens l8- Under some conditions, it would no-t be necessary to extend the weight to the full length of the lever, in which case the pawl 31 can be thrown in engagement with the ratchet 30 when the lever is extended a sufficient length. When the weight V21 is elevated by the crank 29,Hthe member 12 will be elevated through engagement with the weight, Vandthe member 11 will be elevatedl through engagement with the flange 20 onl Vthe member-12, and thus the system of. le-

vers is telescoped. v While in the drawings, I have shown the spool' 25 manually operated by the crank 29, it will be understood that Asaid spool may be operated to elevateV the weight by any well known mechanically or electrically actuated device, suchas a motor, operated. 'by a storage .battery or the like.v The Ybracket 2Q isv attached to` the member 10 by a clamp 40, which permits.

the spool 25 to be shifted to different positions to accommodate the position of the aviator. In this case, the member 10 isv providedwith aV plurality of sheaves 39, as'V is shown in detail in .7.

In Figs. 8 to 12 inclus1veI have' shown a modifiedform of lever. VIn this construcf tion, the upper member 10 is provided with a swivel or universal pivot-41 attached to a bracket 43 extending from the Vupper portion of the machine. The. member.10ex.

tends down through an opening 44 in the lower plane 2 which permits the lever t0 have a slight lateral movement independent of the aeroplane. When the tilting ofthe aeroplane becomes excessive, theportion 10 of the. lever will engage the aeroplane at the perimeter of the opening, and will exert a leverage tending to right they aeroplane in the same manner as the'lever shown in Figs. 1 and 2, previously described. The opening 44'is normally closed Vby a sliding platey 45 held in vposition by pins, 46 and springs 47.

Without limiting myself to the precise arrangement shown and described which may be variedwithin the scope of the claims, I claim: .Y

1. In a device for the purposes specied,

the combination with an aeroplane; of a' contractible lever mountedon and extend ing below said aeroplane, and resilient means mounted on said lever and adapted to cushion the drop of the lever when beingextended; and a Vweight mounted on the lower endof said lever.

. 2. vIn afdevice for.y the purposesspecied; the combination with an. aeroplanegof a plurality of telescopic members constituting a levermounted on said aeroplane., Cable mounted von said aeroplane and constitutingattached to the innermost one of said members, a spool mounted on the outermost member and receiving said cable, means for. rotating said spool; and a weight mounted on'the innermost member. Y l

3. In a device for the purposes specified; the combination with an aeroplane; of a plurality of telescopic members pivotally a `contractible and expandible lever; a cable attached to theinnermost one of said members; a spool mounted on the outermost member and receiving said cable; meansv for rotating said spool; and a weight mounted on the lower end of the innermost member.

4I. In a device for the purposes '-speciied,` the combination with an aeroplane; of al plurality of telescopic members `pivotally mounted on said aeroplane; a cable attached to the innermost one of said members; a spool mounted on the outermost members and receiving' said cable; means for rotating said spool; a weight mounted on the lower end of the innermost member; and resilient means connecting two of said members and adapted to arrest the forcerof the weight when the members are extended.

In testimony whereof I aiiix my signature, in presence of two witnesses.

WILLIAM SAINT.

Witnesses:

R. J. MCCARTY, MATrrmw SIEBLER.

Copies of this patent may be obtained forinve cents each, by addressing the Commissioner of Iatents, lashingtom D. C. 

